W DOC AIRBUS | TSM A320F

Failure of an Opposite Channel of the Generator 1 Channel

TASK 24-20-00-810-888-A
Failure of an Opposite Channel of the Generator 1 Channel

1. Possible Causes
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
 B. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 24-20-00-810-863-A
Failure of the Generator 2 Channel
ASM 242202
AMM 24-41-00-740-002
Operational Check of the GAPCU via the CFDS
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 24-41-00-862-002
De-energize the Aircraft Electrical Circuits Supplied from the External Power
AMM 31-60-00-860-001
EIS Start Procedure
AMM 31-60-00-860-002
EIS Stop Procedure
AMM 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-028
Engine Shutdown
AMM 71-00-00-860-814
Shutdown of the Engine
AMM 71-00-00-860-823
Start the Engine (Normal Automatic Start)
3. Fault Confirmation
Subtask 24-20-00-869-106-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN 1 was set to OFF because of a true fault, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-206-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the upper ECAM-DU warning AC BUS 1 FAULT and one of the two CFDS messages:
GEN 1 DELTA CURRENT OTHER CHANNEL or
GEN 1 OVERCURRENT OTHER CHANNEL
NOTE: These CFDS messages can come into view with other CFDS messages related to a delta current or an overcurrent condition of one of the generator channels 1 or 2.
  • in the AC/DC main power center 120VU, do a check of the bus tie feeders for short circuits.
   (1) If there are short circuits:
  • repair them.
   (2) If there is no short circuit:
  • do a check of the feeders for a short to ground, a short circuit or an open circuit condition between terminals R, P, N of the BTC 1 and the AC transfer bus ASM 242202.
     (a) If the feeders are not correct:
  • repair or replace the AC transfer busbars as necessary.
     (b) If the feeders are correct:
  • continues the trouble shooting.
Subtask 24-20-00-865-061-A ** ON A/C NOT FOR ALL
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
122VUELEC/GCU/12XU1T26
Subtask 24-20-00-860-195-C ** ON A/C NOT FOR ALL
C. Energize the aircraft electrical circuit from generator 2 only.
   (1) Loosen and lower the nuts that attach GCU 1, and pull it along its rack to disconnect the electrical connectors.
   (2) In the cockpit, on the ELEC panel 35VU:
  • Push, release and push again the GEN 2 pushbutton switch (3XU2).
   (3) Start engine 2 AMM 71-00-00-860-823.
Subtask 24-20-00-810-207-C ** ON A/C NOT FOR ALL
D. Do this procedure:
  • After five minutes, see if there is a trip.
   (1) If there is a trip:
   (2) If there is no trip:
  • Close the circuit breaker 2XU1 (remove the safety clip and tag).
Subtask 24-20-00-710-148-C ** ON A/C NOT FOR ALL
E. Do this operational test to make sure that the system operates correctly.
   (1) Aircraft Maintenance Configuration
     (a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
     (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
   (2) In the cockpit, on the ELEC panel 35VU:
  • Push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the BITE test of the GAPCU AMM 24-41-00-740-002.
   (4) Start engine 1 AMM 71-00-00-860-823.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • Push the ELEC key to get the ELEC page.
On the lower ECAM DU:
  • The correct electrical parameters of GEN 1 are shown and GEN 1 supplies the AC1 busbar.
Subtask 24-20-00-860-195-F ** ON A/C NOT FOR ALL
F. Energize the aircraft electrical circuit from the generator 2 only.
   (1) Loosen and lower the nuts that attach the GCU 1 and pull it on its rack to disconnect the electrical connectors.
   (2) On the ELEC panel 35VU, push, release and push again the ELEC/GEN 2 pushbutton switch (3XU2).
   (3) Start the engine 2 AMM 71-00-00-710-003.
Subtask 24-20-00-810-207-F ** ON A/C NOT FOR ALL
G. Do this procedure:
  • after five minutes, see if there is a trip.
   (1) If there is a trip:
   (2) If there is no trip:
  • close the circuit breaker 2XU1 (remove the safety clip and tag).
Subtask 24-20-00-710-148-F ** ON A/C NOT FOR ALL
H. Do this operational test to make sure that the system operates correctly.
   (1) Aircraft Maintenance Configuration
     (a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
     (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
   (2) On the ELEC panel 35VU:
  • push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the operational test of the GAPCU AMM 24-41-00-740-002.
   (4) Start the engine 1 AMM 71-00-00-710-003.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • get the ELEC page.
On the lower ECAM DU:
  • the correct electrical parameters of the GEN 1 are shown and the AC1 busbar is supplied by the GEN 1.
5. Close-up
Subtask 24-20-00-860-182-C ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop engine 1 AMM 71-00-00-860-814.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
Subtask 24-20-00-860-182-F ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop the engine 1 AMM 71-00-00-710-028.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:18 UTC
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